EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.56 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e853-il-1000000.txt Download as CSV file: xf-e853-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E853 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3321 0.09680 0.09534 -0.0420 1.0000 0.0083
-10.500 -0.3365 0.09149 0.09005 -0.0437 0.9998 0.0085
-10.250 -0.3357 0.08567 0.08424 -0.0468 0.9990 0.0086
-10.000 -0.3351 0.07964 0.07821 -0.0503 0.9982 0.0087
-9.750 -0.3338 0.07369 0.07227 -0.0539 0.9971 0.0089
-9.500 -0.3371 0.06612 0.06471 -0.0584 0.9960 0.0089
-9.250 -0.3569 0.05191 0.05050 -0.0663 0.9950 0.0088
-9.000 -0.3861 0.03801 0.03641 -0.0783 0.9923 0.0085
-8.750 -0.3995 0.03088 0.02910 -0.0884 0.9862 0.0085
-8.500 -0.4036 0.02595 0.02394 -0.0961 0.9773 0.0085
-8.250 -0.3948 0.02141 0.01916 -0.1008 0.9708 0.0088
-8.000 -0.3853 0.01842 0.01597 -0.1021 0.9598 0.0090
-7.750 -0.3664 0.01591 0.01327 -0.1039 0.9510 0.0093
-7.500 -0.3382 0.01312 0.01023 -0.1074 0.9454 0.0098
-7.250 -0.3554 0.01719 0.01304 -0.1068 0.9460 0.0049
-7.000 -0.3182 0.01631 0.01204 -0.1093 0.9406 0.0047
-6.750 -0.2826 0.01345 0.00887 -0.1120 0.9331 0.0044
-6.500 -0.2465 0.01193 0.00714 -0.1145 0.9221 0.0043
-6.250 -0.2136 0.01090 0.00591 -0.1160 0.9070 0.0044
-6.000 -0.1848 0.01020 0.00500 -0.1166 0.8904 0.0044
-5.750 -0.1580 0.00972 0.00437 -0.1165 0.8742 0.0046
-5.500 -0.1326 0.00899 0.00342 -0.1163 0.8588 0.0056
-5.250 -0.1062 0.00870 0.00302 -0.1161 0.8449 0.0077
-5.000 -0.0800 0.00828 0.00260 -0.1159 0.8323 0.0237
-4.750 -0.0533 0.00810 0.00239 -0.1159 0.8208 0.0342
-4.500 -0.0267 0.00785 0.00219 -0.1158 0.8099 0.0554
-4.250 -0.0001 0.00749 0.00196 -0.1159 0.7997 0.1015
-4.000 0.0262 0.00699 0.00172 -0.1161 0.7904 0.1840
-3.750 0.0526 0.00644 0.00149 -0.1164 0.7816 0.2930
-3.500 0.0796 0.00609 0.00137 -0.1166 0.7734 0.3778
-3.250 0.1072 0.00602 0.00131 -0.1166 0.7656 0.4144
-3.000 0.1351 0.00596 0.00126 -0.1167 0.7580 0.4375
-2.750 0.1630 0.00596 0.00123 -0.1168 0.7513 0.4570
-2.500 0.1911 0.00593 0.00121 -0.1169 0.7444 0.4761
-2.250 0.2189 0.00596 0.00118 -0.1169 0.7382 0.4864
-2.000 0.2472 0.00596 0.00116 -0.1170 0.7319 0.4959
-1.750 0.2751 0.00598 0.00115 -0.1171 0.7262 0.5064
-1.500 0.3034 0.00598 0.00116 -0.1172 0.7206 0.5185
-1.250 0.3315 0.00600 0.00116 -0.1173 0.7150 0.5289
-1.000 0.3595 0.00603 0.00116 -0.1174 0.7100 0.5376
-0.750 0.3878 0.00602 0.00117 -0.1175 0.7048 0.5443
-0.500 0.4159 0.00606 0.00118 -0.1176 0.6998 0.5506
-0.250 0.4440 0.00608 0.00119 -0.1178 0.6952 0.5565
0.000 0.4723 0.00608 0.00121 -0.1179 0.6903 0.5628
0.250 0.5003 0.00612 0.00124 -0.1180 0.6857 0.5690
0.500 0.5284 0.00614 0.00128 -0.1181 0.6812 0.5755
0.750 0.5566 0.00616 0.00131 -0.1182 0.6763 0.5823
1.000 0.5843 0.00620 0.00135 -0.1183 0.6710 0.5894
1.250 0.6123 0.00621 0.00139 -0.1183 0.6647 0.5969
1.500 0.6398 0.00625 0.00144 -0.1183 0.6580 0.6049
1.750 0.6675 0.00626 0.00149 -0.1183 0.6511 0.6132
2.000 0.6947 0.00632 0.00154 -0.1182 0.6434 0.6225
2.250 0.7223 0.00632 0.00161 -0.1182 0.6351 0.6321
2.500 0.7493 0.00637 0.00168 -0.1181 0.6251 0.6424
2.750 0.7760 0.00643 0.00174 -0.1179 0.6144 0.6538
3.000 0.8035 0.00645 0.00183 -0.1179 0.6054 0.6662
3.250 0.8305 0.00650 0.00192 -0.1178 0.5956 0.6795
3.500 0.8572 0.00656 0.00203 -0.1176 0.5845 0.6944
3.750 0.8836 0.00662 0.00214 -0.1173 0.5699 0.7105
4.000 0.9096 0.00671 0.00226 -0.1170 0.5525 0.7282
4.250 0.9334 0.00692 0.00241 -0.1163 0.5190 0.7480
4.500 0.9559 0.00721 0.00262 -0.1153 0.4745 0.7705
4.750 0.9745 0.00780 0.00296 -0.1137 0.4018 0.7961
5.000 0.9902 0.00859 0.00346 -0.1116 0.3173 0.8269
5.250 1.0030 0.00946 0.00401 -0.1089 0.2279 0.8697
5.500 1.0140 0.01001 0.00442 -0.1057 0.1632 1.0000
5.750 1.0312 0.01082 0.00491 -0.1040 0.1060 1.0000
6.000 1.0511 0.01142 0.00533 -0.1028 0.0737 1.0000
6.250 1.0719 0.01193 0.00573 -0.1017 0.0520 1.0000
6.500 1.0930 0.01241 0.00612 -0.1007 0.0378 1.0000
6.750 1.1141 0.01286 0.00652 -0.0996 0.0274 1.0000
7.000 1.1351 0.01331 0.00697 -0.0985 0.0199 1.0000
7.250 1.1526 0.01400 0.00757 -0.0968 0.0080 1.0000
7.500 1.1689 0.01477 0.00836 -0.0948 0.0042 1.0000
7.750 1.1872 0.01535 0.00899 -0.0932 0.0036 1.0000
8.000 1.2025 0.01602 0.00973 -0.0910 0.0032 1.0000
8.250 1.2142 0.01686 0.01067 -0.0882 0.0030 1.0000
8.500 1.2237 0.01785 0.01178 -0.0850 0.0029 1.0000
8.750 1.2306 0.01902 0.01309 -0.0816 0.0028 1.0000
9.000 1.2368 0.02031 0.01450 -0.0782 0.0028 1.0000
9.250 1.2419 0.02180 0.01612 -0.0748 0.0028 1.0000
9.500 1.2500 0.02317 0.01760 -0.0720 0.0028 1.0000
9.750 1.2596 0.02450 0.01906 -0.0697 0.0028 1.0000
10.000 1.2721 0.02551 0.02016 -0.0678 0.0027 1.0000
10.250 1.2827 0.02680 0.02156 -0.0658 0.0027 1.0000
10.500 1.2949 0.02783 0.02268 -0.0640 0.0026 1.0000
10.750 1.3049 0.02916 0.02412 -0.0622 0.0026 1.0000
11.000 1.3143 0.03053 0.02560 -0.0604 0.0025 1.0000
11.250 1.3199 0.03253 0.02776 -0.0583 0.0025 1.0000
11.500 1.3249 0.03457 0.02995 -0.0563 0.0024 1.0000
11.750 1.3278 0.03687 0.03243 -0.0544 0.0024 1.0000
12.000 1.3291 0.03934 0.03508 -0.0525 0.0024 1.0000
12.250 1.3267 0.04229 0.03823 -0.0507 0.0024 1.0000
12.500 1.3216 0.04559 0.04174 -0.0490 0.0024 1.0000
12.750 1.3157 0.04895 0.04529 -0.0477 0.0024 1.0000
13.000 1.3083 0.05258 0.04911 -0.0468 0.0024 1.0000
13.250 1.2962 0.05696 0.05370 -0.0462 0.0024 1.0000
13.500 1.2837 0.06157 0.05850 -0.0462 0.0024 1.0000
13.750 1.2661 0.06718 0.06433 -0.0468 0.0025 1.0000
14.000 1.2499 0.07294 0.07029 -0.0480 0.0025 1.0000
14.250 1.2318 0.07941 0.07695 -0.0500 0.0025 1.0000
14.500 1.2130 0.08650 0.08419 -0.0529 0.0025 1.0000
14.750 1.1925 0.09458 0.09245 -0.0568 0.0025 1.0000
15.000 1.1714 0.10353 0.10157 -0.0617 0.0025 1.0000
15.250 1.1496 0.11356 0.11176 -0.0677 0.0026 1.0000
15.500 1.1268 0.12500 0.12336 -0.0750 0.0026 1.0000
15.750 1.1035 0.13785 0.13635 -0.0831 0.0026 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER E853 AIRFOIL (e853-il)